CN107140181A - A kind of wing of imitative beetle elytrum - Google Patents
A kind of wing of imitative beetle elytrum Download PDFInfo
- Publication number
- CN107140181A CN107140181A CN201710443781.5A CN201710443781A CN107140181A CN 107140181 A CN107140181 A CN 107140181A CN 201710443781 A CN201710443781 A CN 201710443781A CN 107140181 A CN107140181 A CN 107140181A
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- CN
- China
- Prior art keywords
- wing
- wing body
- cantilever
- beetle elytrum
- imitative
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
Abstract
The invention discloses a kind of wing of imitative beetle elytrum, belong to technical field of aerospace.A kind of wing of imitative beetle elytrum, it is characterised in that：The wing of the imitative beetle elytrum includes one group of cantilever and wing body, and one end of cantilever is fixed on fuselage, and the other end is connected by free hinge with wing body.Compared with prior art, the present invention can eliminate interference of the wing to VTOL while horizontal flight effect is ensured, with the characteristic adaptively adjusted using physical principle, also it is manually operable simultaneously, speed, sensitivity, fault-tolerant ability, security and the lasting hours underway for flying control reaction can be effectively improved, have the advantages that mechanism is coordinated, simple in construction, with low cost, reliability is high, adaptability is good, can be widely applied to the fields such as man-carrying aircraft or unmanned plane.
Description
Technical field
The present invention relates to a kind of wing of imitative beetle elytrum, belong to technical field of aerospace.
Background technology
Manned vehicle can be divided into fixed-wing and the major class of rotary wings two, and fixed-wing is common in Horizontal Take-off and Landing aircraft（As sprayed
Gas formula passenger plane）, and rotary wings are common in vertically taking off and landing flyer（Such as helicopter）.The technical merit just reached at present is come
Say, Fixed Wing AirVehicle can be easy to operate with high-speed flight, but need to rely on runway landing.Rotary-wing aircraft can vertically rise
Drop, is not required to rely on runway landing, strong adaptability, but mechanism is lacked of proper care, and manipulation is complicated, and flying speed is slow, and fuel efficiency is low.
At present, vertically taking off and landing flyer is mainly shown as also in the presence of the inherent shortcoming that some can not overcome：（1）Flight speed
Degree has the limit.Velocity of sound is necessarily less than by wing tip absolute velocity to be limited, the theoretical velocity of rotary-wing aircraft is public no more than 420
In/hour.（2）Reliability is low.Rotor blade waves generation mechanical oscillation, and adding the abrasion of hinge does not make reliability always not
Such as Fixed Wing AirVehicle.（3）Roll stability is poor.Both sides rotor lift is uneven to cause rotary-wing aircraft to occur roll,
It will topple in seconds out of control.（4）Manipulation is complicated.The rotor of helicopter had both provided the mobility of flight, while also making
Into the complexity of flight manipulation.So that manipulation load is far longer than fixed wing aircraft, the probability of human error is increased.（5）
It can not do big.Rotor diameter and rotating speed are limited by tip velocity no more than velocity of sound, and the general maximum of rotor diameter is exactly ten
Several meters, aircraft size is limited, it is impossible to done more.（6）Flight mechanism is lacked of proper care.Although helicopter has developed nearly 70 years, still
In flight mechanism inaccurate coordination, be filled with geneogenous contradiction.（7）Using the contradiction of fixed-wing.It is many novel combined
Vertically taking off and landing flyer is attempted to use fixed-wing, but faces that small area fixed-wing effect is limited and large area fixed-wing can be to hanging down
Downwash flow during straight landing causes the contradiction blocked.
In a word, the drawbacks described above of vertically taking off and landing flyer from wing should take into account VTOL meet again level fly
Two kinds of offline mode of row and the contradiction produced.And do not there is a kind of wing more effectively to solve contradiction described above at present.
The content of the invention
The technical problem to be solved in the present invention be how to solve vertically taking off and landing flyer need to be while taking into account VTOL and water
The contradiction produced during two kinds of state of flights of flat flight.
In order to solve the above technical problems, the present invention proposes a kind of wing of imitative beetle elytrum, the wing is to imitate beetle sheath
Wing Functional Design, deploys when being mainly manifested in into level flight condition, switchs to draw in during hovering flight state.It includes one group
Cantilever and wing body, one end of cantilever are fixed on fuselage, and the other end is connected by hinge with wing body, form basic aircraft shape
State.To meet aerodynamics and meeting flight demand, the wing body is installed for zero-incidence, and section and the aerofoil profile of conventional fixed-wing are cut
Face is identical.There is synchronous limit structure in the wing body, the scope of wing body upset can be controlled and make left and right both wings upset synchronous.The machine
The mechanical device of manual control can be set in the wing, manually can control or aid in wing body to overturn；Wing body is made using rigid large area wing
The wing carry substantially reduce, lift is greatly improved, while can guarantee that flight needed for stability.The axis of cantilever hinge flies with level
Line direction is parallel, with vertical direction angle is 0 ° when wing body is turned over down completely, to ensure during horizontal development natural stress；Wing body is complete
On flattening is kept when turning over, that is, level or basic horizontal are kept, to meet maximum lift during aircraft horizontal flight；The length of cantilever
Degree need to ensure that wing body reserves enough spaces between fuselage after turning over down completely, and reduction is blocked to downwash flow, general wing body
Inner side is more than the 1/2 of body width with body spacing.The wing body can be collapsible or telescopic structure, deploy whole wing
When can break through limitation of the fuselage height to wing length, so as to improve airborne vehicle lift, the folding of wing body or flexible using normal
Rule mode is realized.
Compared with prior art, the present invention can eliminate shadow of the wing to VTOL while horizontal flight demand is ensured
Ring, and the characteristic that can be adaptively adjusted using physical principle simultaneously, while be also manually operable, winged control can be effectively improved
Speed, sensitivity, fault-tolerant ability, security and the lasting hours underway of reaction are low with mechanism coordination, simple in construction, cost
The advantages of honest and clean, reliability is high, adaptability is good, can be widely applied to the fields such as man-carrying aircraft or unmanned plane.
Brief description of the drawings
Fig. 1 is to turn under the present invention to fold schematic diagram.
Fig. 2 is horizontal development schematic diagram of the present invention.
Fig. 3 is that the present invention is in rounding state schematic diagram using folding synchronous limit structure embodiment wing.
Fig. 4 is that the present invention is in its fully unfolded position schematic diagram using folding synchronous limit structure embodiment wing.
Label in figure：1- fuselages, 2- cantilevers, 3- wing bodies, 4- position-limit mechanisms.
Embodiment
The embodiment to the present invention is further described in detail below in conjunction with the accompanying drawings, unreceipted skill in embodiment
Art or product are prior art or can be by buying the conventional products obtained.
Embodiment 1：As Figure 1-4, the present invention proposes a kind of wing of imitative beetle elytrum, and the wing is to imitate beetle sheath
Wing Functional Design, deploys when being mainly manifested in into state of flight, is drawn in when leaving state of flight.It include one group of cantilever 2 with
Wing body 3, one end of cantilever 2 is fixed on the fuselage 1, and the other end is connected by hinge with wing body 3, forms basic aircraft shape
State.To meet aerodynamics and meeting flight demand, the wing body 3 is installed for zero-incidence, section and conventional solid Airfoil Sections
It is identical.There is synchronous limit structure 4 in the wing body 3, the scope of the upset of wing body 3 can be controlled and make left and right both wings upset synchronous.Should
Wing sets mechanical artificial control device, manually can control or aid in wing body 3 to overturn；Wing body 3 uses rigid large area aerofoil profile, just
Property the big aerofoil wing carry and be substantially reduced, lift is greatly improved, while can guarantee that its required stability.The axis of the hinge of cantilever 2
It is parallel with horizontal flight direction, with vertical direction angle be 0 ° when wing body 3 is turned over down completely, with ensure during horizontal development rationally by
Power；Wing body 3 completely on flattening is kept when turning over, to meet topology requirement during aircraft horizontal flight；The length of cantilever 2 needs to ensure
Wing body inner side and body spacing is body width 2/3, is blocked with reducing to downwash flow when wing body 3 is turned over down completely.
Embodiment 2：As Figure 1-4, the present invention proposes a kind of wing of imitative beetle elytrum, and the wing is to imitate beetle sheath
Wing Functional Design, deploys when being mainly manifested in into state of flight, is drawn in when leaving state of flight.It include one group of cantilever 2 with
Wing body 3, one end of cantilever 2 is fixed on the fuselage 1, and the other end is connected by hinge with wing body 3, forms basic aircraft shape
State.To meet aerodynamics and meeting flight demand, the wing body 3 is installed for zero-incidence, section and conventional solid Airfoil Sections
It is identical.There is synchronous limit structure 4 in the wing body 3, the scope of the upset of wing body 3 can be controlled and make left and right both wings upset synchronous.Should
Wing sets conventional mechanical manual controller, manually can control or aid in wing body 3 to overturn；Wing body 3 uses the rigid large area wing
Type, the big aerofoil wing of rigidity, which is carried, to be substantially reduced, and lift is greatly improved, while can guarantee that its required stability.The hinge of cantilever 2
Axis is parallel with horizontal flight direction, when wing body 3 is turned over down completely with vertical direction angle be 0 °, it is reasonable during horizontal development to ensure
Stress；Wing body 3 completely on flattening is kept when turning over, to meet topology requirement during aircraft horizontal flight；The length of cantilever 2 needs to protect
It is equal to body width with body spacing on the inside of wing body when card wing body 3 is turned over down completely, downwash flow is blocked with reducing.Wing body can
For accordion structure, length during whole wing expansion is set to be more than fuselage height, the folding of wing body is folded using conventional mechanical
Mode is realized.
Embodiment 3：As Figure 1-4, the present invention proposes a kind of wing of imitative beetle elytrum, and the wing is to imitate beetle sheath
Wing Functional Design, deploys when being mainly manifested in into state of flight, is drawn in when leaving state of flight.It include one group of cantilever 2 with
Wing body 3, one end of cantilever 2 is fixed on the fuselage 1, and the other end is connected by free hinge with wing body 3, forms basic aircraft
Form.To meet aerodynamics and meeting flight demand, the wing body 3 is installed for zero-incidence, and section is cut with conventional solid wing
Face is identical.There is synchronous limit structure 4 in the wing body 3, the scope of the upset of wing body 3 can be controlled and make left and right both wings upset synchronous.
The wing sets conventional mechanical manual controller, manually can control or aid in wing body 3 to overturn；Wing body 3 uses rigid large area
Aerofoil profile, the big aerofoil wing of rigidity, which is carried, to be substantially reduced, and lift is greatly improved, while can guarantee that its required stability.The hinge of cantilever 2
Axis it is parallel with horizontal flight direction, when wing body 3 is turned over down completely with vertical direction angle be 0 °, to ensure to close during horizontal development
Manage stress；Wing body 3 completely on flattening is kept when turning over, to meet topology requirement during aircraft horizontal flight；The length of cantilever 2 is needed
Ensure wing body 3 when turning over down completely on the inside of wing body with 1.2 times that body spacing is body width, to reduce the screening to downwash flow
Gear.Wing body is telescopic structure, length during whole wing expansion is more than fuselage height, the folding retractable of wing body is using normal
Rule mechanical-stretching mode is realized.
The technology contents of the present invention are described above in conjunction with accompanying drawing, but protection scope of the present invention be not limited to it is described
In content, the knowledge that one skilled in the relevant art possesses, the premise of present inventive concept can also not departed from
Under the technology contents of the present invention are made a variety of changes, within the spirit and principles of the invention, any modification for being made, etc.
With replacement, improvement etc., it should be included in the scope of the protection.
Claims (10)
1. a kind of wing of imitative beetle elytrum, it is characterised in that：The wing is to imitate beetle elytrum Functional Design, and it includes one group
Cantilever（2）With wing body（3）, cantilever（2）One end be fixed on fuselage（1）On, the other end passes through hinge and wing body（3）Connection；Institute
State wing body（2）Cantilever can be surrounded（2）Hinge freely rotate, can be automatically performed down in the air according to flight operating mode and turn over vertical
Or on turn it is flat.
2. the wing of imitative beetle elytrum according to claim 1, it is characterised in that：The wing body（3）Installed for zero-incidence,
Section can select the aerofoil profile of existing fixed-wing.
3. the wing of imitative beetle elytrum according to claim 1, it is characterised in that：The wing body（3）On have synchronous spacing
Mechanism（4）.
4. the wing of imitative beetle elytrum according to claim 1, it is characterised in that：The machine of manual control can be set in the wing
Tool device.
5. the wing of imitative beetle elytrum according to claim 1, it is characterised in that：The wing body（3）Use the big face of rigidity
Product aerofoil profile.
6. the wing of imitative beetle elytrum according to claim 1, it is characterised in that：The cantilever（2）The axis of hinge with
Horizontal flight direction is parallel.
7. the wing of imitative beetle elytrum according to claim 1, it is characterised in that：The wing body（2）When turning over down completely with
Vertical direction angle is 0 °.
8. the wing of imitative beetle elytrum according to claim 1, it is characterised in that：The wing body（2）Protected when being turned on completely
Hold flattening.
9. the wing of imitative beetle elytrum according to claim 1, it is characterised in that：The cantilever（2）Length need ensure
Wing body（3）In fuselage after turning over down completely（1）Between reserve enough spaces, general wing body（3）Inner side and body（1）Spacing is more than
Body（1）The 1/2 of width.
10. the wing of imitative beetle elytrum according to claim 1, it is characterised in that：The wing body（3）Can to be collapsible or
Telescopic structure.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710443781.5A CN107140181A (en) | 2017-06-13 | 2017-06-13 | A kind of wing of imitative beetle elytrum |
| PCT/CN2018/090417 WO2018224033A1 (en) | 2017-06-09 | 2018-06-08 | Aircraft with imitation beetle elytron wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710443781.5A CN107140181A (en) | 2017-06-13 | 2017-06-13 | A kind of wing of imitative beetle elytrum |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107140181A true CN107140181A (en) | 2017-09-08 |
Family
ID=59782645
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710443781.5A Pending CN107140181A (en) | 2017-06-09 | 2017-06-13 | A kind of wing of imitative beetle elytrum |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107140181A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108706093A (en) * | 2018-04-28 | 2018-10-26 | 云南同硕环保科技有限公司 | A kind of wing is equipped with the plate wing machine of large-scale winglet |
| WO2018224033A1 (en) * | 2017-06-09 | 2018-12-13 | 昆明鞘翼科技有限公司 | Aircraft with imitation beetle elytron wings |
| CN112943253A (en) * | 2021-02-02 | 2021-06-11 | 中国海洋大学 | Double-wing type seabed polymetallic nodule collecting device |
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| US20030089821A1 (en) * | 2000-04-13 | 2003-05-15 | Miralles Carlos T. | Payload delivery system |
| CN101712379A (en) * | 2009-07-14 | 2010-05-26 | 北京航空航天大学 | Folding small-sized unmanned aerial vehicle |
| US7770839B2 (en) * | 2007-12-18 | 2010-08-10 | National Institute Of Advanced Industrial Science And Technology | Flight machinery |
| CN102233950A (en) * | 2010-04-24 | 2011-11-09 | 靳文勇 | Vertical takeoff and landing miniature aircraft |
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| CN106005402A (en) * | 2016-06-18 | 2016-10-12 | 夏建国 | Flying saucer type hypersonic stealth jet aircraft capable of realizing vertical take-off and landing |
| CN206939051U (en) * | 2017-06-13 | 2018-01-30 | 昆明鞘翼科技有限公司 | A kind of wing of imitative beetle elytrum |
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2017
- 2017-06-13 CN CN201710443781.5A patent/CN107140181A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030089821A1 (en) * | 2000-04-13 | 2003-05-15 | Miralles Carlos T. | Payload delivery system |
| US7770839B2 (en) * | 2007-12-18 | 2010-08-10 | National Institute Of Advanced Industrial Science And Technology | Flight machinery |
| CN101712379A (en) * | 2009-07-14 | 2010-05-26 | 北京航空航天大学 | Folding small-sized unmanned aerial vehicle |
| CN102233950A (en) * | 2010-04-24 | 2011-11-09 | 靳文勇 | Vertical takeoff and landing miniature aircraft |
| CN105711811A (en) * | 2016-01-27 | 2016-06-29 | 北京航空航天大学 | Wing folding mechanism |
| CN106005402A (en) * | 2016-06-18 | 2016-10-12 | 夏建国 | Flying saucer type hypersonic stealth jet aircraft capable of realizing vertical take-off and landing |
| CN206939051U (en) * | 2017-06-13 | 2018-01-30 | 昆明鞘翼科技有限公司 | A kind of wing of imitative beetle elytrum |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018224033A1 (en) * | 2017-06-09 | 2018-12-13 | 昆明鞘翼科技有限公司 | Aircraft with imitation beetle elytron wings |
| CN108706093A (en) * | 2018-04-28 | 2018-10-26 | 云南同硕环保科技有限公司 | A kind of wing is equipped with the plate wing machine of large-scale winglet |
| CN108706093B (en) * | 2018-04-28 | 2023-09-12 | 昆明鞘翼科技有限公司 | Plate wing machine |
| CN112943253A (en) * | 2021-02-02 | 2021-06-11 | 中国海洋大学 | Double-wing type seabed polymetallic nodule collecting device |
| CN112943253B (en) * | 2021-02-02 | 2023-01-10 | 中国海洋大学 | Double-wing type seabed polymetallic nodule collecting device |
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Legal Events
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170908 |
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| RJ01 | Rejection of invention patent application after publication |